Enclosed jacking insert

ABSTRACT

A case assembly is provided. The case assembly comprises a first flange and a spot face in the first flange. The spot face has a D-shaped perimeter. A jacking insert is disposed in the spot face and has a D-shaped geometry. A threaded cylinder extends from the jacking insert into the first flange. A jacking insert is also provided. The jacking insert comprises a flat portion having a D-shaped geometry and a cylindrical portion having an internal thread configured to interface with a bolt.

CROSS-REFERENCE TO RELATED APPLICATION

This application is a divisional of U.S. Ser. No. 14/600,239, filed Jan.20, 2015, entitled “ENCLOSED JACKING INSERT,” which is herebyincorporated by reference in its entirety.

FIELD OF INVENTION

The present disclosure relates to gas turbine engines, and, morespecifically, to a jacking insert configured for disassemblinginterference snaps affixing a gas-turbine-engine case.

BACKGROUND

Cases on gas turbine engines may be assembled and fixed usinginterference snaps on adjacent flanges. The disassembly of a snap fitmay involve jack screws, which thread into one member and push againstthe adjoined member. Thus, the adjacent flanges may be separated using ajack screw. A jacking insert may include a threaded cylinder attached toa small flange that takes the jacking load. The flange is sandwichedbetween the flanges of the components snapped together (e.g., adjacentsegments of an engine case). The jacking feature may sit recessed in oneof the two flanges to be snap-fit together. The recess is typicallyeither circular or rectangular.

A circular jacking feature is not fixed against rotation within therecess and may spin when the jacking screws are in use. In manyinstances a second wrenching feature may be used to prevent a circularjacking feature from spinning. If the spot face is rectangular, the slotis usually cut through the flange so that it is easy to manufacture.However, in this manner, the thickness of the case flange that is fullhoop is reduced and compromises the structural integrity of the caseflange.

SUMMARY

A case assembly comprises a flange and a recess in the flange. Therecess is defined by a spot face surrounded by a D-shaped wall. Ajacking insert comprises a back plate disposed in the recess with aD-shaped geometry. A threaded cylinder extends from the back plate intothe flange.

The case assembly further comprises a second flange that is snap fittedto the first flange. The jacking insert is at least partially betweenthe first flange and the second flange. A bolt is configured tointerface with the threaded cylinder. The bolt is configured to pressthe first flange and the second flange away from one another in responseto the bolt entering the jacking insert. The spot face comprises acomplete hoop around the jacking insert. The spot face has a contouredperimeter configured to limit rotation of the jacking insert. A bulkheadis pressed against the first flange and covers the spot face. A bolt isconfigured to pass through the jacking insert and an opening defined bythe bulkhead.

A gas turbine engine comprises a static frame component with a firstflange. A low-pressure compressor is aft of the static frame component.A case is disposed around the low-pressure compressor and located aft ofthe static frame component. The case includes a second flange. A jackinginsert is between the first flange and the second flange.

The gas turbine engine further comprises a spot face in at least one ofthe first flange and the second flange with the jacking insert disposedin the spot face. The spot face comprises a contoured perimeter matchinggeometry of the jacking insert. The geometry of the jacking insert isD-shaped. A threaded cylinder extends from the jacking insert into thefirst flange. The second flange that is snap fitted to the first flange.A bolt is configured to interface with the threaded cylinder. The boltis configured to press the first flange away from the second flange inresponse to the bolt entering the jacking insert. The spot facecomprises a complete hoop around the jacking insert.

A jacking insert comprises a flat portion having a D-shaped geometry anda cylindrical portion having an internal thread configured to interfacewith a bolt.

The D-shaped geometry is configured to interact with a spot face tolimit rotation of the jacking insert. The D-shaped geometry comprises asemicircular half and a square half.

The foregoing features and elements may be combined in variouscombinations without exclusivity, unless expressly indicated otherwise.These features and elements as well as the operation thereof will becomemore apparent in light of the following description and the accompanyingdrawings. It should be understood, however, the following descriptionand drawings are intended to be exemplary in nature and non-limiting.

BRIEF DESCRIPTION OF THE DRAWINGS

The subject matter of the present disclosure is particularly pointed outand distinctly claimed in the concluding portion of the specification. Amore complete understanding of the present disclosure, however, may bestbe obtained by referring to the detailed description and claims whenconsidered in connection with the figures, wherein like numerals denotelike elements.

FIG. 1 illustrates a cross-sectional view of an exemplary gas turbineengine, in accordance with various embodiments;

FIG. 2 illustrates a jacking insert with a D-shaped back plate, inaccordance with various embodiments;

FIG. 3 illustrates a case flange with a jacking insert recessed into theflange between bolt holes, in accordance with various embodiments;

FIG. 4 illustrates a cross sectional view of a case bolted to a staticframe component, in accordance with various embodiments; and

FIG. 5 illustrates a cross sectional view of a case assembly snap fittedtogether with a bolt and a jacking insert for unsnapping the caseassembly, in accordance with various embodiments.

DETAILED DESCRIPTION

With reference to FIG. 1, a gas turbine engine 20 is provided. Gasturbine engine 20 may be a two-spool turbofan that generallyincorporates a fan section 22, a compressor section 24, a combustorsection 26 and a turbine section 28. Alternative engines may include,for example, an augmentor section among other systems or features. Inoperation, fan section 22 can drive coolant (e.g., air) along a bypassflow-path B while compressor section 24 can drive coolant along a coreflow-path C for compression and communication into combustor section 26then expansion through turbine section 28. Although depicted as aturbofan gas turbine engine 20 herein, it should be understood that theconcepts described herein are not limited to use with turbofans as theteachings may be applied to other types of turbine engines includingthree-spool architectures.

Gas turbine engine 20 may generally comprise a low speed spool 30 and ahigh speed spool 32 mounted for rotation about an engine centrallongitudinal axis A-A′ relative to an engine static structure 36 viaseveral bearing systems 38, 38-1, and 38-2. It should be understood thatvarious bearing systems 38 at various locations may alternatively oradditionally be provided, including for example, bearing system 38,bearing system 38-1, and bearing system 38-2.

Low speed spool 30 may generally comprise an inner shaft 40 thatinterconnects a fan 42, a low-pressure compressor 44 and a low-pressureturbine 46. Inner shaft 40 may be connected to fan 42 through a gearedarchitecture 48 that can drive fan 42 at a lower speed than low speedspool 30. Geared architecture 48 may comprise a gear assembly 60enclosed within a gear housing 62. Gear assembly 60 couples inner shaft40 to a rotating fan structure. High speed spool 32 may comprise anouter shaft 50 that interconnects a high-pressure compressor 52 andhigh-pressure turbine 54. A combustor 56 may be located betweenhigh-pressure compressor 52 and high-pressure turbine 54. A mid-turbineframe 57 of engine static structure 36 may be located generally betweenhigh-pressure turbine 54 and low-pressure turbine 46. As used herein,“mid-turbine frame” refers to a non-rotating or static structure betweenthe high-pressure turbine 54 and low-pressure turbine 46. In three-spoolengines having an intermediate turbine, a mid-turbine frame may belocated between any of the high-pressure turbine, the low-pressureturbine, and/or the intermediate turbine. Mid-turbine frame 57 maysupport one or more bearing systems 38 in turbine section 28. Innershaft 40 and outer shaft 50 may be concentric and rotate via bearingsystems 38 about the engine central longitudinal axis A-A′, which iscollinear with their longitudinal axes. As used herein, a“high-pressure” compressor or turbine experiences a higher pressure thana corresponding “low-pressure” compressor or turbine.

The core airflow C may be compressed by low-pressure compressor 44 thenhigh-pressure compressor 52, mixed and burned with fuel in combustor 56,then expanded over high-pressure turbine 54 and low-pressure turbine 46.Mid-turbine frame 57 includes airfoils 59, which are in the core airflowpath. Airfoils 59 may be formed integrally into a full-ring,mid-turbine-frame stator and retained by a retention pin. Turbines 46,54 rotationally drive the respective low speed spool 30 and high speedspool 32 in response to the expansion.

Gas turbine engine 20 may be, for example, a high-bypass ratio gearedaircraft engine. In various embodiments, the bypass ratio of gas turbineengine 20 is greater than about six (6). In various embodiments, thebypass ratio of gas turbine engine 20 is greater than ten (10). Invarious embodiments, geared architecture 48 is an epicyclic gear train,such as a star gear system (sun gear in meshing engagement with aplurality of star gears supported by a carrier and in meshing engagementwith a ring gear) or other gear system. Geared architecture 48 can havea gear reduction ratio of greater than about 2.3 and low-pressureturbine 46 has a pressure ratio that is greater than about five (5). Invarious embodiments, the bypass ratio of gas turbine engine 20 isgreater than about ten (10:1). In various embodiments, the diameter offan 42 may be significantly larger than that of the low-pressurecompressor 44. Low-pressure turbine 46 pressure ratio may be measuredprior to inlet of low-pressure turbine 46 as related to the pressure atthe outlet of low-pressure turbine 46 prior to an exhaust nozzle. Itshould be understood, however, that the above parameters are exemplaryof various embodiments of a suitable geared architecture engine and thatthe present disclosure contemplates other turbine engines includingdirect drive turbofans.

Engine static structure includes multiple case components that areinterference fit together. Some case components of engine staticstructure 36, i.e., those that are interference fit, can be separatedfrom one another using a jacking insert and screw. A jacking insert is athreaded female interface that provides a thread for a bolt. The boltuses the thread to bottom out against another surface and press againstthe surface. In that regard, jacking inserts are used, in conjunctionwith a bolt, to separate tightly fitting components.

With reference to FIG. 2, a jacking insert 201 is shown. Jacking insert201 includes back plate 205 made up of a round portion 217 and a squareportion 215 opposite the round portion 217. Threaded cylinder 220 ofjacking insert 201 includes a tapered tip 221. Opening 207 extendscompletely through jacking insert 201. Jacking insert 201 is made from alightweight metal, e.g., aluminum or other metals. Opening 207 containsthreads 222 to convert angular motion of a bolt or screw into linearmotion. Jacking insert 201 has a back plate 205 with sidewall 223 ofback plate 205 having a D-shaped geometry. The outer perimeter ofjacking insert 201 defined by sidewall 223 and has 4 edges. Three of thefour sides define the boundary of square portion 215, and the fourthside defines the boundary of round portion 217. Round portion 217 isessentially circular. Square portion 215 is essentially square but canhave rounded corners and/or edges between sides. The D-shaped geometryof jacking insert 201 interfaces with a flange recess, as described infurther detail below.

With reference to FIG. 3, a flange 206 is illustrated with a jackinginsert 201 disposed in a recess between bolt holes 209. Flange 206contacts static frame component 210. Static frame component 210 issimilar to engine static structure 36 of FIG. 1. Jacking insert 201 isrecessed into flange 206 with the recess of flange 206 defined bycontoured wall 213 and spot face 203. Contoured wall 213 has a D-shapedcontour to match the geometry of back plate 205. Spot face 203 is arecessed, flat surface located on flange 206. Jacking insert 201contacts spot face 203 of flange 206 so that back plate 205 is flush orrecessed relative to the surface of flange 206 surrounding spot face 203outside of contoured wall 213. Spot face 203 is an impression in flange206 having contoured wall 213 bounding spot face 203 on all sides. Thecontoured wall 213 has a contour to match the geometry of back plate 205of jacking insert 201 and constrain jacking insert 201 from rotation.

Back plate 205 of jacking insert 201 has an asymmetric perimeter. Forexample, jacking insert 201 has a D-shaped perimeter comprising a roundportion 217 and a square portion 215. Round portion 217 extends ashorter distance D1 from opening 207 than the distance D2 than squareportion 215 extends from opening 207. Opening 207 is threaded to accepta screw and allow separation of components that are snap fit together,for example, multiple case pieces. Ghosted line 211 illustrates theshape of a jacking insert that would result if a square portionsymmetric to square portion 215 replaced round portion 217. As shown byghosted line 211, jacking insert would extend beyond the boundary ofsurface 219 such that contoured wall 213 of flange 206 would not definea complete hoop of flange material around jacking insert 201.

The constraint against rotation is implemented by the interface betweenthe contoured wall 213 around a recess in flange 206 and jacking insert201 inserted in the recess. Contoured wall 213 holds square portion 215of jacking insert 201 in place as a bolt is screwed or otherwise placedinto jacking insert 201, as described in further detail below. Thesidewall of jacking insert 201 contacts contoured wall 213 of flange206. Contoured wall 213 forms an unbroken, complete hoop around jackinginsert 201 so that material of flange 206 encircles the sidewall of backplate 205.

With reference to FIG. 4, case assembly 200 comprises a case 212 boltedto a bulkhead 216 and a static frame component 210 as illustrated. Case212 can be disposed around low-pressure compressor 44 of FIG. 1, forexample. Case 212 is bolted to static frame component 210 at a forwardlocation of low-pressure compressor 44. Case assembly 200 is illustratedso that the cross section of flange 206 along line B-B′ in FIG. 2 isincluded in area 214 of FIG. 3. Bolt 202 is configured to rotate aboutaxis 204. Axis 204 is also be centrally located in bolt hole 209. Case212 has flange 206 that is coupled to bulkhead 216 and flange 208 ofstatic frame component 210.

With reference to FIG. 5, case assembly 200 including case 212 press fittogether with static frame component 210 is shown. Case assembly 200 isillustrated to include the cross section of flange 206 and jackinginsert 201 along line C-C′ in FIG. 2. Recess 225 is defined by spot face203 and contoured wall 213 of flange 206. Back plate 205 of jackinginsert 201 is disposed within recess 225 and between bulkhead 216 andflange 206. Flange 206 is retained against bulkhead 216 and static framecomponent 210 by a snap fit. The snap fit may require large forces tounsnap during disassembly.

Bolt 224 is inserted into threaded cylinder 220 of jacking insert 201and screwed into threaded cylinder 220. Bolt 224 may screw throughjacking insert 201 and extend through clearance opening 226 in bulkhead216. Bolt 224 may then bottom out against flange 208 and urge flange 206and flange 208 away from one another. The separating force applied bybolt 224 pressing against flange 208 unsnaps any snap fittings andfurthers disassembly of the engine. The anti-rotation characteristics ofjacking insert 201 recessed in flange 208 enables bolt 224 to screw intojacking insert 201 without the use of a second tool to prevent rotation.Jacking insert 201 may be replaced when damaged and prevent replacementof case 212 or static frame component 210.

Benefits, other advantages, and solutions to problems have beendescribed herein with regard to specific embodiments. The scope of thedisclosure, however, is provided in the appended claims.

What is claimed is:
 1. A gas turbine engine, comprising: a static framecomponent comprising a first flange; a low-pressure compressor aft ofthe static frame component; a case around the low-pressure compressorand aft of the static frame component, the case comprising a secondflange; and a jacking insert between the first flange and the secondflange.
 2. The gas turbine engine of claim 1, further comprising arecess defined by at least one of the first flange and the second flangewith the jacking insert disposed in the recess.
 3. The gas turbineengine of claim 2, wherein the recess is defined by a contoured sidewallmatching a geometry of the jacking insert.
 4. The gas turbine engine ofclaim 3, wherein the geometry of the jacking insert is D-shaped.
 5. Thegas turbine engine of claim 1, further comprising a threaded cylinderextending from the jacking insert into the first flange.
 6. The gasturbine engine of claim 5, wherein the second flange is snap fitted tothe first flange.
 7. The gas turbine engine of claim 6, furthercomprising a bolt configured to interface with the threaded cylinder. 8.The gas turbine engine claim 7, wherein the bolt is configured to pressthe first flange away from the second flange in response to the boltentering the jacking insert.
 9. The gas turbine engine of claim 2,wherein the flange comprises a complete hoop around the recess.
 10. Ajacking insert, comprising: a back plate having a D-shaped geometry; anda cylindrical portion having an internal thread configured to interfacewith a bolt.
 11. The jacking insert of claim 10, wherein the D-shapedgeometry is configured to interact with a contoured wall to limitrotation of the jacking insert.
 12. The jacking insert of claim 10,wherein the D-shaped geometry comprises a round portion and a squareportion.